A Review on a Reassess Swot up on Airfoil Stall and Flow Separation Delay for a Range of Limitations Associated with Aerodynamics and Wing Profile.
In this paper study of stall delay at higher angle of attacks the flow gets separated at leading edge, When pressure increases in the flow and velocity direction gradually decreases the speed of the boundary layer to zero and disengages from the surface. To recover from stall, stall delay can occur on airfoils. The flow separation is an undesirable phenomenon for fluid machine wings due to decreased lifting force and increased drag force. The objective of the present study is to separate the flow from stall delay by using different airfoils, by changing mechanisms, angle of attacks. Numerical simulations and Experiments have been carried out to observe the effects of the different shapes of the airfoil leading edges. With the help of any mechanism like vortex generators, Due Selig model, Periodic Excitation, Synthetic Jet Actuators, active flow control mechanism, Acoustic perturbation ,Piezoelectric Actuators ,Oscillatory blowing, fixtures or the mounting devices, separation bubble concept, "Wheeler" vortex generator boundary Layer control(BLC) methods, Laser Doppler Velocimetry (LDV), periodic vortex shredding, Gurney Flap, Digital Particle Image Velocimetry which are focused on flow should reattaches to the surface at the above maximum Mach numbers and Reynolds numbers by changing the span wise and shape wise of the airfoil for stall delay